Class / Patent application number | Description | Number of patent applications / Date published |
415124100 | Runner supported portion engages shaft transmission train (e.g., peripheral gear drive, etc.) | 47 |
20090003992 | Reduced gearbox size by separate electrically powered engine oil system - An accessory system for use in a gas turbine engine, which system includes a gearbox adapted to be arranged radially outward of a main axis of the gas turbine engine and inside a nacelle, one or more engine accessories respectively connected to and driven by the gearbox, and a gas turbine engine oil system driven by a source other than the gearbox. | 01-01-2009 |
20090041575 | Driving Apparatus for a Wave Power Device - Driving apparatus for a wave power device, in which a turbine is placed in a substantially stationary open tubular element, the tubular element extending through the water surface into the water, and in which the amount of water flowing into and out of the tubular element due to a varying wave height around the tubular element, has to pass the turbine; alternatively, the tubular element being placed substantially horizontally below the water surface, a flow of water passing through it, the turbine being connected to a supported turbine shaft, and the turbine shaft being provided with a co-rotating eccentric part, the eccentric part being surrounded by a freely rotatable eccentric bearing connected to the eccentric part, and the eccentric bearing forming the driving part of a fluid pump. | 02-12-2009 |
20110206498 | EPICYCLIC GEARBOX - An epicyclic gear train includes planetary gears rotatably mounted on spindles supported by an annular carrier and including axially spaced apart forward and aft sets of output teeth extending radially outwardly from a planetary gear hub and axially spaced apart forward and aft roller bearings disposed between planetary gears and spindles. The forward and aft roller bearings are axially aligned with or adjacent to spaced apart forward set of output teeth and input gear respectively. A ring gear meshes with forward set of output teeth and an external gear meshes with aft set of output teeth. An input gear fixedly attached to hub aft of aft set of output teeth and engaged with a sun gear. The output teeth, input gear, ring gear, external gear, and sun gear may all be helical. A turbofan gas turbine engine may include counter-rotatable first and second fan stages driven by a low pressure turbine through the gear train. | 08-25-2011 |
20120288358 | CONTRA-ROTATING PROPELLER SYSTEM FOR AN AIRCRAFT TURBINE ENGINE - A contra-rotating propeller system for an aircraft turbine engine, including a free power turbine including a first rotor and a second rotor contra-rotating relative to the first rotor, a first contra-rotating propeller and a second contra-rotating propeller to be rotated about a longitudinal axis of the propeller system relative to a stator of the system, and a mechanical transmission device. The mechanical transmission system is provided between the first propeller and the second propeller. | 11-15-2012 |
20130039746 | TURBOCOMPRESSOR AND TURBOREFRIGERATOR - Provided is a turbocompressor ( | 02-14-2013 |
20130309069 | PITCH BEARING WITH A GEAR SEGMENT IN A WIND TURBINE - A segmented gear plate configured to be removably connected to a pitch bearing of a wind turbine has been described. The pitch bearing is present between a rotor hub and a plurality of blades. The pitch bearing axially pivots the plurality of blades between different pitch angles. The pitch bearing includes an inner bearing ring and an outer bearing ring rotatably interconnected to each other. The segmented gear plate is removably connected to at least one of the inner bearing ring or the outer bearing ring by at least one connecting element. The segmented gear plate having a plurality of gear teeth, the plurality of gear teeth configured to allow the rotation of a drive shaft of a motor to achieve different pitch angles. | 11-21-2013 |
20130315715 | ENERGY SAVING DEVICE ROTATING HALF CIRCLE AND TURNING BACK WITH HELP OF GRAVITY - An energy saving device rotating a half circle and turning back with the help of gravity is revealed. In the first half cycle of a circle movement, a transmission shaft of a motor rotor is controlled to rotate and further drive a first rotating shaft rotating in one direction by a first speed change gear mechanism. The transmission shaft synchronously drives the motor rotor to rotate a half circle, from a lowest position to a highest position on a circumference of the circle. In the other half cycle, the transmission shaft of the motor rotor stops rotating and the motor rotor returns from the highest position to the lowest position with the help of gravity. Thus the half circle rotation of the motor rotor is completed and the first rotating shaft is driven to rotate in one direction continuously so as to achieve energy saving effect. | 11-28-2013 |
20140003915 | LOW NOISE COMPRESSOR ROTOR FOR GEARED TURBOFAN ENGINE | 01-02-2014 |
20140127000 | GAS TURBINE ACCESSORY GEARBOX INCORPORATING DECOUPLING MEANS - A gas turbine AGB has a front lateral face, a rear lateral face opposite from the front lateral face, and a peripheral rim closing the box. At least one gear train is mounted in the AGB and is made up of a plurality of gearwheels meshing together, and designed to be coupled to a drive shaft for driving an accessory. The AGB further comprises, mounted between a central shaft carrying each gearwheel and the drive shaft, a decoupling unit for decoupling the accessory and constituted by a dog clutch having axial teeth co-operating with complementary teeth of the central shaft. The dog clutch includes internal fluting engaged with the corresponding external fluting of the drive shaft. The decoupling unit is controlled by an electric actuator acting on the movement of a plunger pin having one end co-operating with an outer helical groove in the dog clutch. | 05-08-2014 |
20140178180 | FUNDAMENTAL GEAR SYSTEM ARCHITECTURE - A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system. | 06-26-2014 |
20140205438 | RELATIONSHIP BETWEEN FAN AND PRIMARY EXHAUST STREAM VELOCITIES IN A GEARED GAS TURBINE ENGINE - Please replace the abstract with the following rewritten abstract. No new matter has been added. | 07-24-2014 |
20140205439 | GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION - A gas turbine engine includes a housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. A shaft provides a rotational axis. A hub is operatively supported by the shaft. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively. | 07-24-2014 |
20140234078 | METHOD FOR SETTING A GEAR RATIO OF A FAN DRIVE GEAR SYSTEM OF A GAS TURBINE ENGINE - A gas turbine engine includes a fan section including a fan rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.5. A bypass ratio is greater than about 11.0. | 08-21-2014 |
20140286755 | RING GEAR MOUNTING ARRANGEMENT WITH OIL SCAVENGE SCHEME - A turbine engine includes a fan section including a plurality of fan blades, a turbine section, and an epicyclic gear train coupled between the turbine section and the fan section for providing a speed reduction between turbine section and the fan section. The epicyclic gear train includes a plurality of intermediate gears. A carrier supports the plurality of intermediate gears. A sun gear meshes with the plurality of intermediate gears and a ring gear surrounding and meshing with the plurality of intermediate gears. The ring gear includes first and second portions that each have an inner periphery with teeth. The first and second portions of the ring gear have an outer circumferential surface opposite the teeth that provides a first thickness, a second thickness greater than the first thickness and axially inward from the first thickness, and a flange extending radially away from the axis. An epicyclic gear train for a turbine engine and method of designing an epicyclic gear train are also disclosed. | 09-25-2014 |
20140314546 | TURBINE ENGINE GEARBOX MOUNT WITH MULTIPLE FUSE JOINTS - A turbine engine assembly includes a turbine engine case, a gearbox and a plurality of mounts connecting the gearbox to the case. Each of the mounts includes a linkage and a fuse joint. The linkage extends towards the case substantially in a first direction. The fuse joint is configured to substantially prevent movement between the gearbox and the case when the fuse joint is subject to loading less than a threshold, and to permit a constrained movement between the gearbox and the case when the loading is greater than the threshold. The fuse joint of a first of the mounts has a different configuration than the fuse joint of a second of the mounts. | 10-23-2014 |
20140369818 | PLANETARY GEAR SYSTEM ARRANGEMENT WITH AUXILIARY OIL SYSTEM - A gas turbine engine includes a fan, a speed reduction device driving the fan and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input. A stationary first bearing receives lubricant from the lubricant input and has a first race in which lubricant flows and a second race. A second bearing for rotation is within the first bearing including a first opening in registration with the first race such that lubricant may flow from the first race through the first opening into a first conduit. There is a rotating carrier for supporting at least one planetary gear. The second bearing extends from the rotating carrier about an axis. A first spray bar is disposed on the carrier. The second bearing has a second opening in registration with the second race and a second conduit for passing lubricant to the spray bar. | 12-18-2014 |
20150071765 | SUPERCHARGER TRANSMISSION - A supercharger transmission includes a first chamber having timing gears operatively disposed therein. A second chamber has transmission gears operatively disposed therein. An oil fill level is defined in the second chamber. A bearing retention wall is disposed between the first chamber and the second chamber. The bearing retention wall includes a return port to allow fluid communication between the first chamber and the second chamber. The return port is an aperture defined in the bearing retention wall below the oil fill level. The bearing retention wall also includes a crosstalk port to allow fluid communication between the first chamber and the second chamber. The crosstalk port is an aperture defined in the bearing retention wall above the oil fill level. | 03-12-2015 |
20150300197 | GAS TURBINE ENGINE WITH GEARED ARCHITECTURE - A geared architecture for a gas turbine engine comprises a fan shaft and a fan supported on the fan shaft and defining a bypass flow ratio greater than about six. A frame supports the fan shaft. A gear system drives the fan shaft. The gear system has a gear reduction ratio of greater than or equal to about 2.3. A torque frame at least partially supports the gear system. An input is coupled to the gear system. A downstream turbine is coupled to rotatably drive the input coupling. The downstream turbine defines a pressure ratio that is greater than about five (5). | 10-22-2015 |
20150300207 | GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE - A gas turbine engine comprises a gear train defined along an engine axis. A spool along the engine axis drives the gear train, and includes a low stage count downstream turbine. A fan rotates at a fan speed about the engine axis and drives the downstream turbine through the gear train. The fan speed is less than a speed of the downstream turbine. A core is surrounded by a core housing defined about the engine axis. A fan nacelle is mounted around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A bypass ratio defined by the fan bypass passage airflow divided by airflow through the core is greater than about ten (10). | 10-22-2015 |
20150308283 | TURBOMACHINE STARTER OIL FILTRATION SYSTEM - A starter configured for use with a turbomachine includes a housing defining a cavity, a transmission operative to convert an airflow into rotational motion for starting an engine, wherein the cavity is configured to hold a quantity of starter oil for lubricating at least a portion of the transmission, and an oil filter disposed in fluid communication with the starter oil. | 10-29-2015 |
20150308288 | IMPELLER RETENTION APPARATUS - An impeller retention apparatus is provided and includes a bearing element, a rotatable shaft, which is rotatably supported within an outer body by the bearing element, an impeller disposed about and coupled to the shaft to rotate with the shaft and a preload spacer disposed along the shaft between the impeller and the bearing element, the preload spacer comprising an elastic element which biases the impeller away from the bearing element in an axial direction along the shaft. | 10-29-2015 |
20150308350 | MULTI-AXIS ACCESSORY GEARBOXES OF MECHANICAL DRIVE SYSTEMS AND GAS TURBINE ENGINES INCLUDING THE SAME - Gas turbine engines including multi-axis accessory gearboxes of mechanical drive systems are provided. The gearbox comprises a housing, a drive shaft, bevel pinion and drive shaft bevel gears, and a side bevel gear set operable to directly at least one side accessory device. Housing is disposed about a towershaft operatively coupled to main engine shaft and operable to rotate about a first axis. Drive shaft is skewed to main shaft and operable to rotate about a second axis that intersects the first axis at a first angle. Bevel pinion gear is mounted on the towershaft. Drive shaft bevel gear is mounted on the drive shaft. Side bevel gear set comprises an input gear meshing with one or more side bevel gears each having a side bevel gear axis at a second angle to the first axis and independently positionable relative to input gear. Second angle is independent of other angles. | 10-29-2015 |
20150308878 | STARTER OIL QUANTITY INDICATION SYSTEM - A starter can be configured for use with a turbomachine and includes a housing defining a cavity, wherein the cavity is configured to hold a quantity of starter oil, and a temperature sensor disposed within the cavity and configured to sense a temperature within the housing. A system includes a starter for a turbomachine as described herein and a computing apparatus configured to receive signals from the temperature sensor and to determine if the temperature within the housing indicates a sufficient quantity of starter oil. A method for determining oil quantity in a starter includes receiving a temperature signal from a temperature sensor disposed within the starter, determining an oil temperature within the starter based on comparing the temperature signal, and determining if a sufficient amount of oil is present in the starter based on comparing predetermined temperature operational values to the oil temperature. | 10-29-2015 |
20150330331 | RAM AIR TURBINE DRIVESHAFT GEAR AND BEARING ARRANGEMENT - A ram air turbine is presented that includes a turbine having a blade and a turbine shaft, a strut removably coupled to the turbine, wherein the strut has a gearbox section and a drive section, a turbine shaft with a bevel gear oriented perpendicularly to the turbine shaft and positioned within the gearbox section of the strut, a driveshaft coupled to the generator and positioned within the drive section of the strut, and a pinion gear that engages with the bevel gear, wherein the pinion gear is secured to the driveshaft by a spanner nut, wherein the pinion gear utilizes a key configured to interact with the keyed joint of the driveshaft. The pinion gear is supported by a pinion bearing that may be press fit onto the pinion gear and by one of the generator bearings. | 11-19-2015 |
20150337842 | CENTRIFUGAL PUMP WITH COALESCING EFFECT, DESIGN METHOD AND USE THEREOF - The invention provides a centrifugal pump, distinctive in that the pump comprises two or more stages; the last stage in the direction of flow has been adapted so that it provides a larger equilibrium droplet size than the upstream stages. Method of designing the pump and use of the pump. | 11-26-2015 |
20150345392 | GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION - A gas turbine engine includes a housing includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A rotor is connected to the hub and supports a compressor section. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively. The radially inner boundary of the core inlet is at a location of a core inlet stator and the radially inner boundary of the compressor section inlet is at a location of the first stage low-pressure compressor rotor. | 12-03-2015 |
20150354399 | GEARED TURBOFAN WITH INTEGRALLY BLADED ROTOR - A gas turbine comprises a compressor module, with a lower pressure compressor section including a plurality of stages, with at least one of the plurality of stages being an integrally bladed rotor. A higher pressure compressor section includes a plurality of stages with at least one of the plurality of stages being an integrally bladed rotor. A fan drive turbine shaft drives a fan rotor through a gear reduction. The fan rotor delivers a portion of air into a bypass duct, and a portion of air into the compressor module. A bypass ratio defined by the volume of air delivered into the bypass duct compared to the volume of air delivered into the compressor module is greater than or equal to about 6.0. | 12-10-2015 |
20150354401 | VANE LEVER ARM FOR A VARIABLE AREA VANE ARRANGEMENT - A variable area vane arrangement includes a stator vane including a shaft having an axis. The vane arrangement also includes a vane lever arm that rotates the stator vane about the axis. The vane lever arm includes a base, a first tab and a second tab. The base is arranged laterally between the first tab and the second tab. The first tab laterally overlaps the base. The second tab includes an aperture and laterally overlaps the base and the first tab. The shaft extends through the aperture and is connected to the base. | 12-10-2015 |
20150369132 | Distributed Engine Accessory Drive - An accessory drive system for an aircraft gas turbine engine is disclosed. The system may comprise an engine case including a core engine cowl and at least a first accessory drive gearbox disposed within the core engine cowl. The at least first accessory drive gearbox may be operatively connected to one or more accessories remotely located therefrom. | 12-24-2015 |
20150377143 | FLEXIBLE COUPLING FOR GEARED TURBINE ENGINE - A gas turbine engine includes a fan shaft arranged along an engine central axis, a frame supporting the fan shaft, a gear system rotatably coupled with the fan shaft, and a flexible coupling at least partially supporting the gear system. The flexible coupling defines, with respect to the engine central axis, a torsional stiffness TS and a lateral stiffness LS such that a ratio of TS/LS is greater than or equal to about 2.0 to reduce loads on the gear system from misalignment of the gear system with respect to the engine central axis. | 12-31-2015 |
20160010562 | GEARED TURBOFAN WITH INTEGRAL FRONT SUPPORT AND CARRIER | 01-14-2016 |
20160025038 | PIVOT DOOR THRUST REVERSER - A geared turbofan engine includes a fan, a low pressure turbine, a geared architecture, and a nacelle. The fan and low pressure turbine are capable of rotation about an axial centerline of the gas turbine engine. The geared architecture connects the fan to be driven by the low pressure turbine. The nacelle is disposed circumferentially around the fan and defines a portion of a bypass flow duct. The nacelle includes a thrust reverser assembly with one or more doors that pivot to block at least a portion of the bypass flow duct in a deployed position. | 01-28-2016 |
20160047273 | Turbofan Engine Main Bearing Arrangement - A turbofan engine ( | 02-18-2016 |
20160053635 | FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE - A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft configured to drive a fan, a support configured to support at least a portion of the fan shaft, the support defining a support transverse stiffness and a support lateral stiffness, a gear system coupled to the fan shaft, and a flexible support configured to at least partially support the gear system. The flexible support defines a flexible support transverse stiffness with respect to the support transverse stiffness and a flexible support lateral stiffness with respect to the support lateral stiffness. The input defines an input transverse stiffness with respect to the support transverse stiffness and an input lateral stiffness with respect to the support lateral stiffness. | 02-25-2016 |
20160061051 | GEARED TURBOFAN WITH THREE TURBINES WITH HIGH SPEED FAN DRIVE TURBINE - A gas turbine engine according to an example of the present disclosure includes a fan section includes, among other things, a fan, a first compressor section, and a second compressor section configured to compress air to a higher pressure than the first compressor section. A first turbine section is configured to drive the second compressor section. A second turbine section is configured to drive the first compressor section. A fan drive turbine section is positioned downstream of the second turbine section. The fan drive turbine section is configured to drive the fan section through a gear reduction. The fan drive turbine section has a first exit area at a first exit point and is configured to rotate at a first speed. The second turbine section has a second exit area at a second exit point and is configured to rotate at a second speed, which is faster than the first speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area. | 03-03-2016 |
20160061052 | GAS TURBINE ENGINE WITH HIGH SPEED LOW PRESSURE TURBINE SECTION - A gas turbine engine according to an example of the present disclosure includes, among other things, a fan having one or more fan blades. A compressor section is in fluid communication with the fan. The compressor section includes a first compressor section and a second compressor section. A turbine section is in fluid communication with the compressor section. The turbine section includes a first turbine section and a second turbine section. The first turbine section has a first exit area at a first exit point and rotates at a first speed. The second turbine section has a second exit area at a second exit point and rotates at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area. | 03-03-2016 |
20160084105 | FAN DRIVE GEAR SYSTEM - A gas turbine engine includes a fan section and a speed change mechanism for driving the fan section. A first fan section support bearing is mounted forward of the speed change mechanism and a second fan section bearing is mounted aft of the speed change mechanism. | 03-24-2016 |
20160097304 | GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE - A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, and a low spool including a low pressure compressor section and a low pressure turbine. A high spool includes a high pressure compressor section. A gear arrangement is defined along an engine axis. The low spool is operable to drive the fan section through the gear arrangement. A mount system includes an aft mount configured to react at least a portion of a thrust load at an engine case generally parallel to an engine axis. | 04-07-2016 |
20160108854 | LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE - A gas turbine engine assembly according to an example of the present disclosure includes, among other things, a fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, a geared architecture configured to drive the fan, a turbine section configured to drive the geared architecture, a compressor section including a first compressor and a second compressor, and an inlet portion forward of the fan. A length of the inlet portion has a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion. A dimensional relationship of L/D is between about 0.2 and about 0.45. | 04-21-2016 |
20160123332 | ROTARY MACHINE - A rotary machine characterized by being equipped with: a rotary drive part; a drive shaft that is rotated about a horizontally extending axis by the rotary drive part; a large gear that is fixed to the drive shaft; a bearing part that rotatably supports the drive shaft, and to which a lubrication oil is supplied; multiple pinions that are driven by being engaged with the large gear; multiple compression parts that are arranged so as to correspond to the multiple pinions and are respectively rotated by the pinions; and a plate that is installed between the bearing part and the large gear and covers at least a portion of the bottom half of the large gear so as to separate the large gear and the bearing part from each other. | 05-05-2016 |
20160146108 | FUEL PUMPING UNIT - A fuel pumping unit has a low pressure centrifugal pump and a high pressure centrifugal pump. In use, the low pressure pump supplies fuel at a boosted pressure to the high pressure pump for onward supply to a fuel metering unit. The pumping unit further has a drive input which drives the low and high pressure pumps. A gear arrangement is operatively located between the drive input and the low and high pressure pumps such that the low and high pressure pumps are driven at different speeds by the drive input. | 05-26-2016 |
20160160875 | GAS TURBINE ENGINE WITH FAN CLEARANCE CONTROL - A fan section for use in a gas turbine engine has a fan rotor with a plurality of blades and an outer fan housing surrounding the plurality of blades. A tip clearance is defined between a radially outer tip of the blades and a radially inner surface of the fan housing. A fan drive shaft drives the rotor. A drive input drives the fan drive shaft. A shifting mechanism shifts a location of the blades relative to the drive input, thereby controlling the tip clearance. A gas turbine engine is also disclosed. | 06-09-2016 |
20160201682 | SPLIT AXIAL-CENTRIFUGAL COMPRESSOR | 07-14-2016 |
20160376911 | ROLLER BEARINGS FOR HIGH RATIO GEARED TURBOFAN ENGINE - A gear system for a geared turbofan engine is disclosed. The gear system includes a sun gear driven by a low spool shaft. The sun gear defines a sun gear diameter. A rotating carrier drives a fan. The carrier defines an outer carrier diameter and an inner carrier diameter. A non-rotating ring gear is also included. The ring gear defines a ring gear diameter and the ring gear diameter is smaller than the outer carrier diameter. A set of planet gears are mounted on corresponding rolling element bearing assemblies. Each roller element bearing assembly is supported within the carrier within a space defined between the carrier outer diameter and the carrier inner diameter. Each of the sun gear, ring gear and planet gears are substantially centered along a gearbox centerline transverse to an engine longitudinal axis and the gear system provides a speed reduction ratio between an input to the sun gear and an output from the carrier between 3:1 and 5:1. A method of creating a gear system for a geared turbofan engine and a geared turbofan system are also disclosed. | 12-29-2016 |
20160376990 | Aircraft Turbomachine Comprising a Heat Exchanger and a Gearbox in a V Configuration - Aircraft turbomachine comprising at least one heat exchanger ( | 12-29-2016 |
20180023471 | GAS TURBINE ENGINE SHAFT ARCHITECTURE AND ASSOCIATED METHOD OF DISASSEMBLY | 01-25-2018 |
20180023481 | MULTI-SPOOL GAS TURBINE ENGINE ARCHITECTURE | 01-25-2018 |